Turn-back type fusing load-reducing force-bearing structure at fan end of low-pressure rotor of engine

A low-pressure rotor and engine technology, which is applied to engine components, machines/engines, mechanical equipment, etc., can solve the problems affecting the safety of the whole engine and the increase of dynamic load, etc., and achieve the effect of increasing stress and optimal structure

Pending Publication Date: 2022-08-05
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0002] Fan blade loss is the most serious failure of a turbofan engine. As the diameter of fan wide-chord blades becomes larger and the number of blades become

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  • Turn-back type fusing load-reducing force-bearing structure at fan end of low-pressure rotor of engine
  • Turn-back type fusing load-reducing force-bearing structure at fan end of low-pressure rotor of engine
  • Turn-back type fusing load-reducing force-bearing structure at fan end of low-pressure rotor of engine

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[0033] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. The described embodiments are some, but not all, of the embodiments of the present invention. The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0034] According to an embodiment of the present invention, the low-pressure rotor fan end foldback type fuse load-reducing bearing structure of the engine of the present inven...

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Abstract

The invention discloses an engine low-pressure rotor fan end turn-back type fusing load reduction bearing structure, and relates to the field of aero-engine structures, the engine low-pressure rotor fan end turn-back type fusing load reduction bearing structure mainly comprises a first bearing part and a second bearing part, a turn-back type conical transition section thin-wall structure is ingeniously designed, the stress at a weak position can be increased while the rigidity requirement is guaranteed, and the service life of the engine low-pressure rotor fan end is prolonged. Fracture fusing occurs under the fan flying loss sudden unbalanced load threshold value, the rigidity and the fracture threshold value are adjusted by changing the thickness and the angle of the conical transition section, and the optimal structure is achieved. The engine supporting structure is simplified, and meanwhile maintenance and replacement are convenient.

Description

technical field [0001] The invention relates to the field of aero-engine structures, in particular to a load-bearing structure, in particular to a fold-back type fuse-cut load-reducing load-bearing structure at the fan end of a low-pressure rotor of an engine. The wall structure can increase the stress at the weak position while ensuring the rigidity requirements, and achieve fracture and fusing under the load threshold. Background technique [0002] The missing fan blade is the most serious fault of the turbofan engine. As the diameter of the wide chord blade of the fan increases and the number of blades decreases, the dynamic load caused by the sudden loss of the fan blade and the unbalance continues to increase, which is a serious problem. Affect the safety of the whole engine. In order to ensure that the engine structure can withstand huge sudden unbalanced loads without safety accidents after the fan blades are lost, one method is to thicken the supporting structure, t...

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Application Information

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IPC IPC(8): F01D21/04F01D25/16
CPCF01D21/045F01D25/162Y02T50/60
Inventor 孙涛冯引利蒋文婷刘棣李佳琦莫古云钟文元
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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